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NACA 63A210 (naca63a210-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 63A210 (naca63a210-il)
Reynolds number: 200,000
Max Cl/Cd: 48.26 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca63a210-il-200000-n5.txt
Download as CSV file: xf-naca63a210-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63A210                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6245   0.08895   0.08388  -0.0145   0.5422   0.0144
 -10.000  -0.6338   0.08065   0.07566  -0.0201   0.5421   0.0143
  -9.750  -0.6483   0.07005   0.06502  -0.0297   0.5421   0.0141
  -9.500  -0.6658   0.06248   0.05733  -0.0367   0.5421   0.0139
  -9.250  -0.6827   0.05700   0.05165  -0.0393   0.5421   0.0139
  -9.000  -0.6935   0.05111   0.04542  -0.0405   0.5421   0.0140
  -8.750  -0.6963   0.04584   0.03964  -0.0407   0.5420   0.0145
  -8.500  -0.6951   0.04115   0.03454  -0.0405   0.5419   0.0151
  -8.250  -0.6825   0.03869   0.03184  -0.0402   0.5418   0.0156
  -8.000  -0.6683   0.03589   0.02869  -0.0397   0.5417   0.0160
  -7.750  -0.6521   0.03313   0.02552  -0.0391   0.5416   0.0164
  -7.500  -0.6334   0.03073   0.02274  -0.0385   0.5415   0.0169
  -7.250  -0.6129   0.02862   0.02028  -0.0379   0.5413   0.0175
  -7.000  -0.5909   0.02673   0.01806  -0.0373   0.5412   0.0182
  -6.750  -0.5677   0.02521   0.01624  -0.0368   0.5411   0.0193
  -6.500  -0.5432   0.02419   0.01496  -0.0363   0.5410   0.0207
  -6.250  -0.5183   0.02318   0.01371  -0.0359   0.5407   0.0214
  -6.000  -0.4955   0.02125   0.01160  -0.0353   0.5405   0.0224
  -5.750  -0.4716   0.02015   0.01040  -0.0348   0.5402   0.0234
  -5.500  -0.4471   0.01932   0.00950  -0.0344   0.5399   0.0247
  -5.250  -0.4223   0.01863   0.00871  -0.0340   0.5397   0.0263
  -5.000  -0.3970   0.01807   0.00807  -0.0337   0.5396   0.0289
  -4.750  -0.3718   0.01748   0.00733  -0.0333   0.5395   0.0306
  -4.500  -0.3476   0.01665   0.00643  -0.0329   0.5394   0.0334
  -4.250  -0.3221   0.01611   0.00583  -0.0326   0.5394   0.0379
  -4.000  -0.2960   0.01570   0.00532  -0.0323   0.5393   0.0441
  -3.750  -0.2702   0.01522   0.00483  -0.0321   0.5392   0.0592
  -3.500  -0.2450   0.01464   0.00442  -0.0319   0.5392   0.0992
  -3.250  -0.2218   0.01370   0.00402  -0.0317   0.5391   0.2219
  -3.000  -0.2003   0.01267   0.00375  -0.0312   0.5391   0.4094
  -2.750  -0.1761   0.01225   0.00366  -0.0306   0.5391   0.5100
  -2.500  -0.1508   0.01203   0.00358  -0.0300   0.5390   0.5713
  -2.250  -0.1254   0.01189   0.00357  -0.0293   0.5390   0.6262
  -2.000  -0.1001   0.01183   0.00361  -0.0286   0.5386   0.6726
  -1.750  -0.0741   0.01184   0.00365  -0.0280   0.5380   0.7043
  -1.500  -0.0473   0.01188   0.00365  -0.0277   0.5373   0.7250
  -1.250  -0.0202   0.01192   0.00365  -0.0274   0.5367   0.7401
  -1.000   0.0071   0.01195   0.00365  -0.0273   0.5363   0.7531
  -0.750   0.0345   0.01201   0.00369  -0.0271   0.5357   0.7659
  -0.500   0.0618   0.01204   0.00371  -0.0270   0.5350   0.7790
   0.000   0.1161   0.01205   0.00376  -0.0266   0.5333   0.8060
   0.250   0.1432   0.01207   0.00382  -0.0263   0.5325   0.8200
   0.500   0.1705   0.01210   0.00390  -0.0261   0.5318   0.8351
   0.750   0.1981   0.01215   0.00401  -0.0259   0.5310   0.8519
   1.000   0.2265   0.01230   0.00420  -0.0260   0.5297   0.8704
   1.250   0.2561   0.01264   0.00457  -0.0263   0.5279   0.8910
   1.500   0.2882   0.01280   0.00479  -0.0272   0.5267   0.9123
   1.750   0.3227   0.01290   0.00496  -0.0286   0.5253   0.9343
   2.000   0.3577   0.01324   0.00536  -0.0303   0.5225   0.9556
   2.250   0.3927   0.01396   0.00615  -0.0322   0.5165   0.9749
   2.500   0.4274   0.01477   0.00704  -0.0341   0.5088   0.9923
   2.750   0.4571   0.01550   0.00788  -0.0350   0.5013   1.0000
   3.000   0.4813   0.01506   0.00768  -0.0344   0.4992   1.0000
   3.250   0.5086   0.01210   0.00493  -0.0333   0.4611   1.0000
   3.500   0.5337   0.01233   0.00496  -0.0330   0.4430   1.0000
   3.750   0.5585   0.01267   0.00535  -0.0326   0.4266   1.0000
   4.000   0.5846   0.01263   0.00556  -0.0322   0.4040   1.0000
   4.250   0.6091   0.01262   0.00540  -0.0316   0.3237   1.0000
   4.500   0.6290   0.01324   0.00544  -0.0306   0.2012   1.0000
   4.750   0.6479   0.01423   0.00586  -0.0296   0.1001   1.0000
   5.000   0.6698   0.01492   0.00634  -0.0288   0.0615   1.0000
   5.250   0.6928   0.01549   0.00690  -0.0281   0.0461   1.0000
   5.500   0.7157   0.01609   0.00752  -0.0274   0.0378   1.0000
   5.750   0.7381   0.01673   0.00818  -0.0266   0.0318   1.0000
   6.000   0.7598   0.01744   0.00896  -0.0257   0.0280   1.0000
   6.250   0.7819   0.01811   0.00972  -0.0248   0.0257   1.0000
   6.500   0.8034   0.01886   0.01055  -0.0239   0.0240   1.0000
   6.750   0.8242   0.01969   0.01148  -0.0229   0.0226   1.0000
   7.000   0.8437   0.02070   0.01254  -0.0217   0.0215   1.0000
   7.250   0.8609   0.02212   0.01403  -0.0202   0.0206   1.0000
   7.500   0.8796   0.02354   0.01555  -0.0189   0.0200   1.0000
   7.750   0.9001   0.02481   0.01696  -0.0179   0.0197   1.0000
   8.000   0.9209   0.02613   0.01845  -0.0169   0.0191   1.0000
   8.250   0.9416   0.02735   0.01989  -0.0160   0.0182   1.0000
   8.500   0.9616   0.02868   0.02140  -0.0150   0.0172   1.0000
   8.750   0.9803   0.03041   0.02336  -0.0139   0.0167   1.0000
   9.000   0.9975   0.03230   0.02550  -0.0126   0.0162   1.0000
   9.250   1.0129   0.03433   0.02779  -0.0113   0.0157   1.0000
   9.500   1.0260   0.03652   0.03025  -0.0098   0.0154   1.0000
   9.750   1.0369   0.03873   0.03272  -0.0082   0.0150   1.0000
  10.000   1.0463   0.04074   0.03492  -0.0067   0.0145   1.0000
  10.250   1.0501   0.04343   0.03781  -0.0049   0.0140   1.0000
  10.500   1.0430   0.04724   0.04196  -0.0025   0.0136   1.0000
  10.750   1.0358   0.04990   0.04499   0.0002   0.0133   1.0000
  11.000   1.0230   0.05325   0.04863   0.0022   0.0132   1.0000
  11.250   1.0067   0.05731   0.05297   0.0029   0.0130   1.0000
  11.500   0.9884   0.06224   0.05813   0.0019   0.0130   1.0000
  11.750   0.9687   0.06830   0.06437  -0.0014   0.0130   1.0000
  12.000   0.9478   0.07563   0.07188  -0.0066   0.0131   1.0000
  12.250   0.9255   0.08379   0.08019  -0.0122   0.0132   1.0000
  12.500   0.9020   0.09329   0.08979  -0.0187   0.0134   1.0000
  12.750   0.8776   0.10418   0.10075  -0.0256   0.0137   1.0000
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